AD 86-16-04 R1

AD Final Rules - DRS_86-16-04_R.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
86-16-04 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; British Aerospace Jetstream Model 3101 Airplanes
Subject:
Inspect Flap Torque Shaft
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/20/1986
Make:
British Aerospace Regional Aircraft
Model:
Jetstream Series 3101
Product Type:
Aircraft
Product Subtype:
Small/Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 86-16-04 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5416

AD NUMBER:   86-16-04 R1

SUBJECT HEADING:   Airworthiness Directives; British Aerospace Jetstream Model 3101 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 20, 1986.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   86-16-04 R1 BRITISH AEROSPACE: Amendment 39-5383 as amended by 39-5416. Applies to Jetstream Model 3101 (all serial numbers) airplanes which have incorporated Arkansas Modification Center, Inc. (AMC) baggage pod Modification STC No. SA5900SW using baggage pod Serial Numbers 003 through 026, 028, 034, 035, 037, and 038.

Compliance: Required within the next 50 landings after the effective date of this AD, unless already accomplished.

NOTE: If landings are not recorded, one hour time-in-service (TIS) equals two landings.

To prevent possible scoring and failure of the two flap torque tubes, and subsequent loss of control of the aircraft, accomplish the following:

(a) Inspect the flap torque shaft in accordance with BAe Alert Service Bulletin (ASB) No. 27-JA850949 dated January 8, 1986, Section 2 B, "Inspection/Repair", Subparagraph (1)

(1) If scored in excess of 0.030 inches in depth, before further flight replace torque shaft with a serviceable shaft.

(2) If scoring does not exceed 0.030 inches in depth,

(i) Before further flight repair in accordance with BAe ASB No. 27- JA850949 dated January 8, 1986, Section 2B, "Inspection/Repair", Subparagraph (3), and

(ii) Inspect for cracks using a dye penetrant inspection to establish integrity of the shaft. If cracks are found, before further flight, replace torque shaft with a serviceable shaft.

(b) Rework panels F21 and F22 in accordance with Arkansas Modification Center, Inc. (AMC) Mandatory Service Bulletin (MSB) No. 25-0001(-1) dated May 13, 1986, Section 2A, "ACCOMPLISHMENT INSTRUCTIONS".

(c) Airplanes may be flown with the flap system rendered inoperative in accordance with FAR 21.197 to a location where this AD may be accomplished.

(d) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Southwest Region, Special Programs Branch, ASW-190, 4400 Blue Mound Road, Post Office Box 1689, Fort Worth, Texas 76101.

All persons affected by this AD may obtain copies of Arkansas Modification Center, Inc., (AMC) Mandatory Service Bulletin (MSB) No. 25-0001(-1) dated May 13, 1986, referred to herein upon request to the Arkansas Modification Center, Inc., Post Office Box 3356, Adams Field, Little Rock, Arkansas 72203, and Alert Service Bulletin No. 27-JA85-0949 dated January 8, 1986, referred to herein upon request to the British Aerospace, Engineering Department, Post Office Box 17414, Dulles International Airport, Washington, D.C. 20041 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

Amendment 39-5383 became effective on August 13, 1986.

This amendment, 39-5416, becomes effective September 20, 1986.

FOOTER: